Optimal Cooperative Guidance Strategies for Aircraft Defense with Impact Angle Constraints
Given the limitations of escape maneuvers and decoy deployment of combat aircraft under missile attacks; active defense dramatically improves the survival chances by launching active defense missiles to intercept incoming missiles. Different from previous work, this paper implemented impact angle co...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
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MDPI AG
2022-11-01
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| Series: | Aerospace |
| Subjects: | |
| Online Access: | https://www.mdpi.com/2226-4310/9/11/710 |
| _version_ | 1797466209873035264 |
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| author | Quancheng Li Tian Yan Mengjing Gao Yonghua Fan Jie Yan |
| author_facet | Quancheng Li Tian Yan Mengjing Gao Yonghua Fan Jie Yan |
| author_sort | Quancheng Li |
| collection | DOAJ |
| description | Given the limitations of escape maneuvers and decoy deployment of combat aircraft under missile attacks; active defense dramatically improves the survival chances by launching active defense missiles to intercept incoming missiles. Different from previous work, this paper implemented impact angle constraints on the defense missile to achieve a better defense effect. The low-cost active defense missile with limited maneuverability is considered to cooperate with the aircraft through three mechanisms, namely two-way cooperation without any predetermined strategy, one-way cooperation with the defense missile employing a linear guidance strategy, and one-way cooperation with independent evasion maneuver for the target. Three optimal cooperative guidance strategies with impact angle constraints were investigated. Finally, a nonlinear two-dimensional model for agents with first-order autopilot dynamics was simulated to verify the performance of the proposed strategies. The simulation results indicated that the cooperative mechanism directly affects the available range of impact angles, and the constraints of a big impact angle can be realized by introducing the nonlinear model parameters and considering the angle variation between the velocity vector and the initial line-of-sight. Furthermore, the two-way cooperative mechanism achieves the best performance and more flexible solutions to accommodate different vehicle maximum overload limits. |
| first_indexed | 2024-03-09T18:32:35Z |
| format | Article |
| id | doaj.art-c3a1f26012f54e4d837cbfb35b5b7b42 |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-09T18:32:35Z |
| publishDate | 2022-11-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-c3a1f26012f54e4d837cbfb35b5b7b422023-11-24T07:24:18ZengMDPI AGAerospace2226-43102022-11-0191171010.3390/aerospace9110710Optimal Cooperative Guidance Strategies for Aircraft Defense with Impact Angle ConstraintsQuancheng Li0Tian Yan1Mengjing Gao2Yonghua Fan3Jie Yan4School of Astronautics, Northwestern Polytechnical University, Xi’an 710072, ChinaUnmanned System Research Institute, Northwestern Polytechnical University, Xi’an 710072, ChinaUnmanned System Research Institute, Northwestern Polytechnical University, Xi’an 710072, ChinaSchool of Astronautics, Northwestern Polytechnical University, Xi’an 710072, ChinaUnmanned System Research Institute, Northwestern Polytechnical University, Xi’an 710072, ChinaGiven the limitations of escape maneuvers and decoy deployment of combat aircraft under missile attacks; active defense dramatically improves the survival chances by launching active defense missiles to intercept incoming missiles. Different from previous work, this paper implemented impact angle constraints on the defense missile to achieve a better defense effect. The low-cost active defense missile with limited maneuverability is considered to cooperate with the aircraft through three mechanisms, namely two-way cooperation without any predetermined strategy, one-way cooperation with the defense missile employing a linear guidance strategy, and one-way cooperation with independent evasion maneuver for the target. Three optimal cooperative guidance strategies with impact angle constraints were investigated. Finally, a nonlinear two-dimensional model for agents with first-order autopilot dynamics was simulated to verify the performance of the proposed strategies. The simulation results indicated that the cooperative mechanism directly affects the available range of impact angles, and the constraints of a big impact angle can be realized by introducing the nonlinear model parameters and considering the angle variation between the velocity vector and the initial line-of-sight. Furthermore, the two-way cooperative mechanism achieves the best performance and more flexible solutions to accommodate different vehicle maximum overload limits.https://www.mdpi.com/2226-4310/9/11/710cooperative guidance strategiesimpact angle constraintsoptimal control theorythree-body engagementzero-effort quantities |
| spellingShingle | Quancheng Li Tian Yan Mengjing Gao Yonghua Fan Jie Yan Optimal Cooperative Guidance Strategies for Aircraft Defense with Impact Angle Constraints Aerospace cooperative guidance strategies impact angle constraints optimal control theory three-body engagement zero-effort quantities |
| title | Optimal Cooperative Guidance Strategies for Aircraft Defense with Impact Angle Constraints |
| title_full | Optimal Cooperative Guidance Strategies for Aircraft Defense with Impact Angle Constraints |
| title_fullStr | Optimal Cooperative Guidance Strategies for Aircraft Defense with Impact Angle Constraints |
| title_full_unstemmed | Optimal Cooperative Guidance Strategies for Aircraft Defense with Impact Angle Constraints |
| title_short | Optimal Cooperative Guidance Strategies for Aircraft Defense with Impact Angle Constraints |
| title_sort | optimal cooperative guidance strategies for aircraft defense with impact angle constraints |
| topic | cooperative guidance strategies impact angle constraints optimal control theory three-body engagement zero-effort quantities |
| url | https://www.mdpi.com/2226-4310/9/11/710 |
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